Helicopter



c. E. DARROW HELICOPTER Filed Sept. 3, 1943 4 Sheets-Sheet l- Inventor y4 c. E. DAROW- ,4

HELICOPTER Filed Sept. 3, 1943 4 Sheets-Sheet 2 q q 1 N m 'm 1 :r

\H\ Inventor diiawelii'efi Farrow M July 39, 1946.

c. E. DARROW HELICOPTER Filed se i. 3, 1945 4 Sheets-Sheet 4 I jlm/entorhrence .zi'flar raw' B? yaw W3) 1 WIi Patented July 30, 1946 UNITEDSTATE HELICOPTER Clarence E. Darrow, Miami, Fla. 7 Application September3, 1943, Serial No. 501,121

2 Claims. 1

The present invention relates to new and use- ,ful improvements inhelicopters, and has for one of its important objects to provide aflying machine of this character comprising a unique arrangement ofrotors driven in opposite directions through the medium of twin engines.

Another very important object of the invention is to provide ahelicopter of the aforementioned character which embodies novelpropulsion and control means.

Other objects of the invention are to provide a helicopter of thecharacter described which will be comparatively simple inconstruction,-strong, durable, reliable in operation, and which may bemanufactured at low cost.

All of the foregoing, and still further objects and advantages of theinvention, will become apparent from a study of the following specification, taken in connection with the accompanying drawing wherein likecharacters of reference designate corresponding parts throughout theseveral views, and wherein:

Figure 1 is a top plan view of a helicopter constructed in accordancewith the present invention.

Figure 2 is a-view in front elevation thereof.

Figure 3 is a View in side elevation of the machine.

Figure 4 is a fragmentary view in vertical 1ongitudinal section, takensubstantially on the line 44 of Figure 2.

Figure 5 is a view inside elevation of the elevator assembly.

Figure 6 is a top plan view of the rudder assembly with portions of thesurfaces broken 1:

away in section, the elevator assembly shown in Figure 5 being omittedfrom the rear end of the fuselage.

Figure 7 is a fragmentary view in horizontal section showing, in topplan, the means for releasably securing the safety flaps in vertical orinoperative position.

Figur 8 is a view principally in horizontal section through thefuselage.

Figure 9 is a cross-sectional view through the forward portion of thefuselage.

Figure 10 is a view in horizontal section on an enlarged scale throughthe elevator assembly.

Referring now to the drawings in detail, it will be seen that theembodiment of the invention which has been illustrated comprises afuselage of suitable dimensions and material which is designatedgenerally by reference numeral I. Landing wheels 2 are provided beneaththe fuselage I. Th forward portion of the fuselage I comprises a cabin3. The forward portion of the fuselage I further includes ananti'clinal'top portion 4. Rising from the apex or peak of the topportion 4 of the fuselage I is a panel 5..

Mounted on the forward portion of the fuselage I is a frame structure 6;The frame structure 6 is transversely elongated and mounted for rotationin opposite directions-on the ends thereof is a pair of rotors I.Engines 8 in thefuselage I drive the rotors I in opposite directions bysuitable means, such as shafts 9,'universal joints I0, gears I I, etcetera.

Safety flaps I2 are hingedly suspended from the upper portion oftheframe structure 6 on opposite sides of the fuselage I.' In theembodiment shown, the safety'flaps I2 are releasably secured in verticalor inoperative position by means including shafts I3 which are journaledin bearings I4 on the frame structure 6 and which are operable fromwithin the cabin 3. As best seen in Figure 7 of the drawings, the shaftsI3 have fixed thereon pairs of spaced fingers I5 which receive the flapslz'therebetween for releasably securing said flaps against swingingmovement and in vertical position. j Mounted on top of theframestructure 6," beneath the inner portions of the rotors I, are pairs ofinverted U frames I6. Series of slats I1 are journaled for verticalswinging adjustment between'the pairs of frames I6 for receiving the airblast or wash from the rotors "1. Bars I8 are pivotally connected to theupper ends of the series of slat I! for actuating said slats: in unison.,Cables I9 fromhandleverslbinthe cabin 3 are connected to the ends ofthe bars IB'for adjusting the slats Il as desired. Two such levers 20are provided, onefor eachset or series of the slats I1.

Built into the fuselage I is a pair of wind tunnels 2!. The tunnels 2|comprise, at their forward end portions, upwardly opening intakes 22(see Fig. 9) on opposite sides of the anticlinal top portion 4 of thefuselage I. Thus, the tunnels 2| are adapted to receive the air blast orwash from the inner portions of the rotors I. The upstanding panel 5prevents air turmoil between the rotors I and the oppositely inclinedsides of the top portion 4 of the fuselage I direct the air into theintakes 22. At an intermediate point, the tunnels 2| merge into a singletunnel 23 (see Fig. 8) which extends to the rear end of the fuselage I.

Mounted on the rear end of the fuselage I is an elevator assembly 24.The assembly 24 inludes a pair of rearwardly projectin Substam 3 tiallyU-shaped brackets 25 which are fixed on V the upper portion of thefuselage l. Journaled in the cabin 3 for actuating the elevators 26.

Also mounted on the rear end of the fuselage I, beneath the elevatorassembly 24, is a rudder assembly 30. The assembly 30 includes a pair'of substantially U-shaped brackets 3| which are It is believed that themany advantages ofa helicopter constructed in accordance with thepresent invention will be readily understood, and although a preferrredembodiment of the machine is as illustrated and described, it is to beunderstood that changes in the details of construction and in thecombination and arrangement of parts may be resorted to which will fallwithin the .scopeof the invention as claimed.

What is claimed is: 1. A helicopter comprising a fuselage including o aforward part provided with an anticlinal roof mounted transversely onthe rear end of the fuselage I. Pivotally mounted for horizonal swingingmovement on the brackets 3| and extending rearwardly therefrom is a gangof spaced, parallel rudders 32. A- bar 33 is pivotally connected to therudders '32 at intermediate points in said rudders for actuating same inunison. Cables '34 connect the bar 33 to therotatable wheel 35 on theswinging column 29 in the cabin 3 for actuating the rudders 32. a

It is thought that the operation of the machine will be readily apparentfrom a consideration of the foregoing. Briefly, the desired lift is hadfrom the oppositely rotating rotors 1, said rotors being actuated bytheir respective enines 8. Forward or backwardmovementis had through themedium of the slats l1. With the slats l1 adjusted to the inclinationshown in Figure 4 of the drawings, thewash or downward blast of air fromthe rotors '1 strikes said slats and drives the machine forwardly. Thespeed is governed by the inclination of the slats I1. With the slats ITin a vertical position, the machine will ascend or descend vertically orhover. Rearward tilting of the slats I! will'cause the machine to travelbackward. As the series of slats are adjustable independently, saidslats may, if desired, be utilized to turn or'as'sist in turning themachine. Air from the'rotors is directed into the intakes 22 of thetunnels 2| by the top portion 4 of the fuselage 'l. The air thus iscaused to enter the tunnels under pressure. This blast of air emerges atthe rear'end of the fuselage l and assists in propelling the machineforwardly. This air also strikes the surfaces 26 -and"32 in amanner tomaterially increase the effectiveness thereof. Should one of the enginesfail, that-side of the machine will, of course, drop. When thisoocurs,';the safety flaps l2 are released and said flaps swing upwardlyto a horizontal positionbeneath the upper portion of the frame structure6 where they are arrested and function asplane to assist thepilot inbringing the craft to a safe landing.

portion having a ridge extending longitudinally of said fuselage, aframe structure mounted on and extending laterally from opposite sidesof the fuselage, rotors mounted on and disposed above said framestructure at opposite sides of the fuselage, means for actuating therotors, a panel rising from and parallel with the ridge of theanticlinal roof portion of the fuselage, between'the rotors,longitudinal air tunnels in the fuselage, said air tunnels includingupturned intakes opening at their upper ends at opposite sides of theanticlinal roof portion of the fuselage and below the inner portions ofthe rotors for receiving the air blasts therefrom, said tunnels openingthrough the rear end of the fuselage, and control surfaces mounted onsaid rear end of the fuselage for receiving the air fromthe tunnels.

2. A helicopter comprising a'fuselage including a forward part providedwith an anticlinal roof portion having a ridge extending longitudilnally' of said fuselage, a frame structure mounted on and extendinglaterally from opposite sides of the fuselage, rotors mounted on anddisposed above said frame structure at oppo ite sides of the fuselage,means for actuating the rotors, a panel rising from and parallel withthejridge of the anticlinal roof portion of the fuselage between therotors, longitudinal air tunnels inthe fuselage, said air tunnelsincluding upturned intakes opening at their upper ends at opposite sidesof the anticlinal roof portion of the fuselage and below the innerportions of the rotors for receiving the air blasts therefrom, saidtunnels opening through the rear end of the fuselage, a series oftransverse slats mounted for vertical swinging adjustment on the framesections 'beneath the inner portion of each rotor and directly abovesaid intakes for receiving the air blasts from said rotors, and meansfor "actuating each series of said slats in unison.

CLARENCE E. DARR'OW.

